39 research outputs found
Modeling of radiative - conductive heat transfer in compositing materials
A layer of composite material is investigated, which is heated one-sidedly with one-dimensional energy transfer accounting for thermal conductivity and radiation. A mathematical model is suggested for non-stationary coefficient thermophysical problem under radiative-conductive heat transfer in a material layer. Temperature dependencies of thermal capacity and thermal conductivity coefficient of composite radio-transparent material have been determined through numerical modeling by solving the coefficient reverse problem of thermal conductivity
Parametric Identification of Thermophysical Properties of Highly Porous Partially Transparent Materials Based on the Solution of a Two-Dimensional Problem of Radiative-Conductive Heat Transfer
History and experience of overcoming thermal barriers in rocket and space technology: 1. Ballistic missiles
Model of the Structure of Fibrous Heat-Insulating Materials for Analyzing Combined Heat Transfer Processes
Determination of the effect of carbon nanosized particles on thermophysical characteristics of polymer composite materials
Parametric and topology optimization of load bearing elements of aircraft fuselage structure
Abstract
This paper presents the weight reduction of load bearing elements of aircraft DA-62 fuselage structure using parametric and topology optimizations methods. The structural analysis of rear part of aircraft fuselage in various load calculation conditions is performed. In the first step using parametric optimization of structure, allow to reduce its mass to 15.84 %. In addition using topology optimization of optimized structure by parametric modeling added mass reduction to 32.87% of total structural mass.</jats:p
Coupled CFD-based Shape Optimization of a Wing of Reusable Space Vehicle of Tourist Class
Abstract
This article proposes an approach to two-stage shape optimization of the wing of tourist class reusable space vehicle. To achieve appropriate lift and drag force levels, CFD-based optimization methods in combination with geometric parametrisation was applied. During the first stage, the optimization focuses on reduction of wing square and providing required velocity during vehicle’s landing. In this case, for improving the aerodynamic and mass characteristics five geometric design variables were used. The second stage of optimization emphasis on drag force minimization in order to enhance the wing shape in assigned design area by means of adjoint discrete method.</jats:p
